US7464508B2 - Self-stiffened panels of preimpregnated composite and manufacturing process for components of such panels - Google Patents
Self-stiffened panels of preimpregnated composite and manufacturing process for components of such panels Download PDFInfo
- Publication number
- US7464508B2 US7464508B2 US10/992,221 US99222104A US7464508B2 US 7464508 B2 US7464508 B2 US 7464508B2 US 99222104 A US99222104 A US 99222104A US 7464508 B2 US7464508 B2 US 7464508B2
- Authority
- US
- United States
- Prior art keywords
- nail
- skin
- panel
- stiffeners
- punches
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related, expires
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/34—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
- B29C70/345—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation using matched moulds
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/40—Shaping or impregnating by compression not applied
- B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
- B29C70/46—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
- B29D99/00—Subject matter not provided for in other groups of this subclass
- B29D99/001—Producing wall or panel-like structures, e.g. for hulls, fuselages, or buildings
- B29D99/0014—Producing wall or panel-like structures, e.g. for hulls, fuselages, or buildings provided with ridges or ribs, e.g. joined ribs
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Definitions
- This invention concerns the manufacture of self-stiffened panels comprised of layers of preimpregnated fibers, and intended for construction of wing panels and fuselage boxes for example.
- FIG. 1 a cross-section of the self-stiffened, preimpregnated composite panel comprised of a base skin 1 , on one face of which are added U-shaped stiffeners 2 placed parallel and side-by-side and each of them separated by an interfacing structure including a nail 3 and a nail-head 4 between them, the nail being formed of two half-nails 3 a and 3 b placed symmetrically, and the nail-head 4 filling in the space remaining between the skin 1 , on the one hand, and the edges adjoining the half-nails 3 a and 3 b , on the other hand, is represented.
- the skin 1 and also the U-shaped stiffeners 2 and the half-nails 3 a and 3 b , are comprised of superimposed plies formed of fabric or layers of carbon fibers preimpregnated with an appropriate resin.
- the stiffeners 2 , the half-nails 3 a and 3 b , and the nail-heads 4 generally run the entire length of the panel.
- An object of the invention is to simplify and perfect the type of panel shown in FIG. 1 .
- the self-stiffened panels that are the subject of this invention are of a type comprised of a skin generally formed by several superimposed plies of preimpregnated carbon fibers, with the addition of U-shaped stiffeners added side-by-side, parts joining the branches of the U that are flattened against said skin with interposition, between the adjoining branches of two adjacent stiffeners, of an interfacing structure commonly called a “nail,” completed by a “nail-head” comprised of a cord of filling resin.
- the present invention aims to simplify and perfect the type of panel with U-shaped stiffeners illustrated in FIG. 1 from the attached drawings whose interfacing structure includes a nail formed of two half-nails placed symmetrically and a nail-head placed between the edges adjoining the half-nails, and involves a particular step of forming the half-nails.
- the subject of the invention is a self-stiffened panel of preimpregnated composite of a type made of a base skin, on one of the faces of which are added and arranged side-by-side U-shaped stiffeners of which the parts joining the branches of the U are flattened against said skin with interposition, between the adjoining branches of two adjacent stiffeners, of an interfacing structure commonly called a “nail,” completed by a “nail-head” comprised of a cord of filling resin, characterized by the fact that said nail is formed from a band with a rectangular section, the skin side edge of which is directly in contact with the adjoining side of said skin, and in that the head of the nail is comprised of two half-nail-heads arranged symmetrically in the angle formed between the skin and the nail.
- said band forming the nail is a solid piece and comprised of at least one ply of preimpregnated carbon fibers.
- said band forming the nail is formed of two components or half-nails, placed side-by-side, each formed of at least one ply of preimpregnated carbon fibers.
- a subject of the invention is a manufacturing process for components of a self-stiffened panel of preimpregnated composite of a type comprised of a base skin on one side of which are added and placed side-by-side U-shaped stiffeners of which the parts connecting the branches of the U are flattened against said skin, with interposition, between the adjoining branches of two adjacent stiffeners, of an interfacing structure commonly called a “nail”, completed by a “nail-head” comprised of a cord of filling resin, said nail being a single piece and said nail-head being comprised of two half-nail-heads placed symmetrically in the angle formed between the skin and said nail, characterized by the following steps:
- the subject of the invention is also a manufacturing process for components of a self-stiffened panel of preimpregnated composite of a type comprised of a base skin on one side which are added and placed side-by-side U-shaped stiffeners of which the parts connecting the branches of the U are flattened against said skin, with interposition, between the adjoining branches of two adjacent stiffeners, of an interfacing structure commonly called a “nail”, completed by a “nail-head” comprised of a cord of filling resin, said nail being made of two half-nails and said nail-head being comprised of two half-nail-heads placed symmetrically in the angle formed between the skin and said nail, characterized by the following steps:
- Such a manufacturing process for panel components is particularly appropriate for implementing panels with very large dimensions.
- the panels of the type according to said first manufacturing method require, during their fabrication, a phase of rotation a unit, specifically the tool bearing the set of U-shaped stiffeners, which poses problems for handling and also tooling, because of their size.
- the panel manufacturing process according to said second manufacturing method avoids all handling of heavy and large units because the rotation operations consist of handling, and notably rotation, only individual punches, one after the other.
- FIG. 1 is a partial cross-section of the self-stiffened panel with the U-shaped stiffeners added to a base skin.
- FIG. 2 is a partial cross-section of a panel from the invention according to the first manufacturing method.
- FIG. 3 illustrates the placement of a ply on a punch with a U-shaped cross-section.
- FIG. 4 illustrates the placement of the nail and two nail half-nail-heads between two punches.
- FIG. 5 illustrates the rotation by 180° of the set of punches from FIG. 4 .
- FIGS. 6 , 7 and 8 illustrate the final steps of placing the stiffeners-nails-nail-heads unit from FIG. 5 on a base skin and withdrawing the punches.
- FIG. 9 is a partial cross-section of a panel from the invention according to the second manufacturing method.
- FIG. 10 illustrates the placement of the half-nails and half-nail-heads for the panel from FIG. 9 on a punch.
- FIG. 11 illustrates the individual rotation by 180° of the punch.
- FIG. 12 illustrates the placement side-by-side after rotation the punches.
- FIGS. 13 to 15 illustrate the final steps of placing the stiffeners-nails-nail-heads unit from FIG. 12 on a base skin and withdrawing the punches.
- the panel includes a base skin 5 , on one face of which are added U-shaped stiffeners 6 , between which is placed a single-piece nail 7 with a rectangular cross-section whose edge 8 is placed directly against the adjoining face of skin 5 with half-nail-heads 9 and 10 filling the spaces arranged in the angles formed between the skin 5 and the nails 7 under the stiffeners 6 .
- FIG. 3 a punch at 11 is shown whose cross-section is U-shaped defining three flat outer surfaces that are orthogonal or parallel to each other; respectively the surfaces 12 and 13 correspond to the two parallel branches of the U and a connecting surface 14 .
- the punch 11 has a length at least equal to that of the stiffeners 6 to be made and is placed in the position of an inverted U for the placement of the superimposed plies shaped in rectangular bands before making up the stiffeners.
- FIG. 15 shows a cross-section of such a superposition made by draping and forming a band whose length is equal to that of the U-shaped stiffener to be made.
- the band 15 is placed astride punch 11 as illustrated, previously coated with a polyethylene film (not shown) to avoid sticking of the band 15 and allowing the later withdrawal of the punch, in order to form under infrared the U-shaped stiffener while flattening the edges of the band 15 on the sides 12 and 13 of the punch; the longitudinal edges of the band are cut to fit the height of the said sides.
- FIG. 4 illustrates the following step of placing side-by-side on a tool 16 the punches 11 coated this way with band 15 , with the interposition between two punches 11 of a nail 7 , previously made by draping one or more plies of preimpregnated carbon fibers and cutting to the dimensions of the sides 12 and 13 of the punches.
- the half-nail-heads 9 and 10 are placed last.
- a bladder (not shown) is placed on the assembly and vacuum is applied to compact the components 7 , 9 , 10 , and 15 , in order to have a surface that is as uniformly flat as possible and without spaces or empty interstices near the nail-nail-head unit.
- the following step consists of rotation by 180° ( FIG. 5 ) the set of punches, and then bringing ( FIG. 6 ) the punches' 11 mounting plate 16 over the basic skin 5 placed on its waiting surface plate 17 .
- the set of punches 11 is placed on the skin 5 ( FIG. 7 ) and, finally, the punches 11 are lifted away one after the other ( FIG. 8 ) in order to obtain an assembly structure, according to FIG. 2 , which it is next appropriate to strengthen in an autoclave in the normal manner.
- FIG. 9 shows a panel from the invention according to the second manufacturing method.
- the panel from FIG. 9 includes a base skin 18 , to one face of which are added U-shaped stiffeners 19 , between which are placed two half-nails 20 and 21 placed side-by-side their entire length, the edges of the half-nails being flattened directly against the adjoining side of skin 18 , the half-nail-heads 22 and 23 filling the spaces set up in the angles formed between the skin 18 and the half-nails 20 and 21 under the stiffeners 19 .
- the two half-nail-heads 22 and 23 are positioned in the empty spaces existing between the band 15 and the half-nails 20 and 21 .
- a bladder (not shown) is placed on the assembly and vacuum is applied to compact the components 20 , 21 , 22 , 23 and 15 .
- the following step is the individual rotation of the punches 11 by 180° as illustrated by the passage from FIG. 10 to FIG. 11 in order for their placement side-by-side ( FIG. 12 ) on a surface plate 24 .
- the assembly of punches 11 is taken-on and lifted using an overhead crane ( FIG. 13 ) in order to be placed ( FIG. 14 ) on the skin 18 previously prepared by draping in a well-known manner and waiting on its surface plate 25 , and, finally, the punches 11 are lifted away one after the other ( FIG. 15 ) in order to obtain an assembly structure, according to FIG. 9 , which it is next appropriate to strengthen in an autoclave in the normal manner.
- Such a process for placing panel components according to FIG. 9 presents the following substantial advantages compared to that necessary for the implementation of the panel according to FIG. 1 :
- the gathering ( FIG. 12 ) of the stiffening components ( 19 ) in the position (U-shaped punches 11 ′ in the upright U position) corresponding to their placement for setting down on the base skin 18 is done by individually rotating the punches after the step of compacting the components 20 , 21 , 22 , 23 and 15 on each punch. Such a manipulation is done easily and does not require unusual equipment.
- the nail-heads 4 can only be put in place and then subjected to compacting on the complete assembly of punches for shaping the stiffeners which must then be in an inverted U position and placed side-by-side. It is then necessary, after compacting all of the punches as a whole, to rotate 180° to put them in position for placement on the base skin 1 .
- This manipulation requires means of sufficient scale and space to perform the rotation of an assembly of large dimensions when it involves a large-size panel.
- the half-nails 20 and 21 are simple flat rectangular bands more simple and easy to implement than the half-nails 3 a and 3 b with flanged edges at the height of the nail-heads 4 , requiring a prior compacting phase.
- step of placing the punches 11 side-by-side on the surface plate illustrated by FIG. 12 can be eliminated by positioning the punches 11 one after the other directly on the skin 18 placed on its surface plate 25 ( FIG. 14 ).
- the type of panel from FIG. 2 is preferably reserved for manufacturing of panels not having overly large dimensions because of the fact that the process for putting the constituent components in place is analogous to that of the panel from FIG. 1 , with the same inconveniences that were just reviewed.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Architecture (AREA)
- Civil Engineering (AREA)
- Structural Engineering (AREA)
- Moulding By Coating Moulds (AREA)
- Laminated Bodies (AREA)
- Reinforced Plastic Materials (AREA)
- Panels For Use In Building Construction (AREA)
Abstract
Description
-
- draping several superimposed plies of preimpregnated carbon fiber to make up said base skin;
- installing and forming on individual punches with a U-shaped section and rounded corners and a length corresponding to that of the U-shaped stiffeners of the panel being made, of at least one reinforcing ply of preimpregnated carbon fibers;
- construction of a nail comprised of a band, the length of which corresponds to that of the U-shaped stiffeners and a width equal to the height of the branches of said U by draping at least one ply of preimpregnated carbon fibers;
- positioning punches side-by-side in inverted U position with interposition of said nail;
- placement of two half-nail-heads for the aforementioned nail on both sides of each nail between the latter and said reinforcing ply;
- compaction of the set of punches thus placed side-by-side;
- 180° rotation of the set of compacted punches;
- positioning of this unit on said base skin in a manner to flatten against the latter a continuous flat surface defined, in part, by the outer side of the parts connecting the branches of the stiffeners' U, and in part by the “nail+nail-head” unit separating two adjacent stiffeners;
- and, finally, withdrawal of said U-shaped punches.
-
- installing and forming on individual punches with a U-shaped cross-section and rounded corners, and a length corresponding to that of the U-shaped stiffeners of the panel being made, of at least one reinforcing ply of preimpregnated carbon fibers;
- construction of half-nails comprised of a band whose length corresponds to that of the U-shaped stiffeners and a width equal to the height of the branches of said U by draping at least one ply of preimpregnated carbon fibers;
- placement of a half-nail on both vertical-sides of each punch covered by said reinforcing ply and in inverted U position, and a half-nail-head inserted between said reinforcing ply and the half-nail at the height of the rounded corner of said punch;
- individual compaction of each punch coated this way;
- individual 180° rotation of the punches;
- then positioning of punches side-by-side on said base skin in a manner to flatten against the latter a continuous flat surface defined, in part, by the outer side of the parts connecting the branches of the stiffeners' U, and in part by the “nail+nail-head” unit separating two adjacent stiffeners;
- and, finally, withdrawal of said U-shaped punches.
Claims (3)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0314254A FR2863198B1 (en) | 2003-12-04 | 2003-12-04 | PRE-IMPREGNED COMPOSITE SELF-RAIDIS PANELS AND METHODS OF PLACING ELEMENTS OF SUCH PANELS |
FR0314254 | 2003-12-04 |
Publications (2)
Publication Number | Publication Date |
---|---|
US20050178083A1 US20050178083A1 (en) | 2005-08-18 |
US7464508B2 true US7464508B2 (en) | 2008-12-16 |
Family
ID=34451722
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US10/992,221 Expired - Fee Related US7464508B2 (en) | 2003-12-04 | 2004-11-18 | Self-stiffened panels of preimpregnated composite and manufacturing process for components of such panels |
Country Status (6)
Country | Link |
---|---|
US (1) | US7464508B2 (en) |
EP (1) | EP1537982B1 (en) |
AT (1) | ATE375856T1 (en) |
CA (1) | CA2487647C (en) |
DE (1) | DE602004009516T2 (en) |
FR (1) | FR2863198B1 (en) |
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US20100068326A1 (en) * | 2006-01-31 | 2010-03-18 | The Boeing Company | Tools for Manufacturing Composite Parts and Methods for Using Such Tools |
US20110195230A1 (en) * | 2004-09-29 | 2011-08-11 | The Boeing Company | Apparatuses, Systems, and Methods for Manufacturing Composite Parts |
US8465613B2 (en) | 2011-08-24 | 2013-06-18 | The Boeing Company | Method and apparatus for fabricating variable gauge, contoured composite stiffeners |
US8557165B2 (en) | 2008-10-25 | 2013-10-15 | The Boeing Company | Forming highly contoured composite parts |
US8601694B2 (en) | 2008-06-13 | 2013-12-10 | The Boeing Company | Method for forming and installing stringers |
US20140374013A1 (en) * | 2013-02-04 | 2014-12-25 | The Boeing Company | Fabrication of Stiffened Composite Panels |
US8974212B2 (en) | 2004-07-26 | 2015-03-10 | The Boeing Company | Systems for manufacturing composite parts with female tools |
US9023265B1 (en) * | 2013-01-28 | 2015-05-05 | The Boeing Company | Systems, tools, and methods for forming corrugated structures and apparatuses including corrugated structures |
US9254619B2 (en) | 2008-05-28 | 2016-02-09 | The Boeing Company | Method and apparatus for fabricating variable gauge, contoured composite stiffeners |
US9387628B2 (en) | 2011-08-24 | 2016-07-12 | The Boeing Company | Method and apparatus for fabricating composite stringers |
US9511520B1 (en) | 2014-08-20 | 2016-12-06 | The Boeing Company | Method, apparatus and device for preventing vacuum bag wrinkling |
US10035300B2 (en) | 2015-06-23 | 2018-07-31 | The Boeing Company | System and method for manufacturing a stiffened composite structure |
US10369740B2 (en) | 2015-07-09 | 2019-08-06 | The Boeing Company | Method of forming a contoured hat stiffener |
US11041477B2 (en) * | 2015-05-01 | 2021-06-22 | Vestas Wind Systems A/S | Reinforcing structure for a wind turbine blade |
US20220314557A1 (en) * | 2021-04-01 | 2022-10-06 | Airbus Operations Sas | Tool for manufacturing a self-stiffened panel, and method for manufacturing a self-stiffened panel using said tool |
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GB0614087D0 (en) | 2006-07-14 | 2006-08-23 | Airbus Uk Ltd | Composite manufacturing method |
DE102008001498B3 (en) * | 2008-04-30 | 2009-08-27 | Airbus Deutschland Gmbh | Method for manufacturing reinforced fiber composite component for aerospace, involves providing forming tool with pre-determined forming section, where forming or supporting element is formed by forming section of forming tool |
FR2986990B1 (en) * | 2012-02-17 | 2014-10-03 | Airbus Operations Sas | SELF-RAIDI PANEL IN COMPOSITE MATERIAL AND METHOD FOR PRODUCING SUCH A PANEL |
FR2997955B1 (en) | 2012-11-13 | 2015-07-03 | Structil | COMPOSITE STRUCTURE FILLING MATERIAL |
WO2014175795A1 (en) * | 2013-04-25 | 2014-10-30 | Saab Ab | A method and a production line for the manufacture of a torsion-box type skin composite structure |
WO2014175799A1 (en) * | 2013-04-25 | 2014-10-30 | Saab Ab | A method and a production line for the manufacture of a torsion-box type skin composite structure |
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US9856008B2 (en) * | 2014-05-19 | 2018-01-02 | The Boeing Company | Composite structure and methods of forming thereof |
IT201700122745A1 (en) * | 2017-10-27 | 2019-04-27 | Salver S P A | Assembly process of parts of an aeronautical wing |
FR3108871A1 (en) | 2020-04-07 | 2021-10-08 | Airbus Operations | PROCESS FOR MANUFACTURING A PREFORM PACKAGED WITH A COMPONENT IN COMPOSITE MATERIAL AND PROCESS FOR MANUFACTURING THE SAID COMPONENT |
CN111923453B (en) * | 2020-06-22 | 2022-01-25 | 成都飞机工业(集团)有限责任公司 | Female die soft film forming tool for internal flatness of mouth-shaped part and control method |
EP4011588A3 (en) | 2020-11-18 | 2022-11-23 | The Boeing Company | Placement of stringer sections preforms on a wing panel preform |
US11780181B2 (en) | 2020-11-18 | 2023-10-10 | The Boeing Company | Multi-lane tows for use with ply-by-ply forming machines |
NL2027407B1 (en) * | 2021-01-26 | 2022-08-19 | Boeing Co | Multi-lane tows for use with ply-by-ply forming machines |
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2003
- 2003-12-04 FR FR0314254A patent/FR2863198B1/en not_active Expired - Fee Related
-
2004
- 2004-11-18 US US10/992,221 patent/US7464508B2/en not_active Expired - Fee Related
- 2004-11-29 AT AT04106144T patent/ATE375856T1/en not_active IP Right Cessation
- 2004-11-29 EP EP04106144A patent/EP1537982B1/en not_active Not-in-force
- 2004-11-29 DE DE602004009516T patent/DE602004009516T2/en active Active
- 2004-12-03 CA CA2487647A patent/CA2487647C/en not_active Expired - Fee Related
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Also Published As
Publication number | Publication date |
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DE602004009516D1 (en) | 2007-11-29 |
EP1537982A1 (en) | 2005-06-08 |
CA2487647C (en) | 2012-04-24 |
US20050178083A1 (en) | 2005-08-18 |
EP1537982B1 (en) | 2007-10-17 |
ATE375856T1 (en) | 2007-11-15 |
DE602004009516T2 (en) | 2008-07-24 |
FR2863198A1 (en) | 2005-06-10 |
CA2487647A1 (en) | 2005-06-04 |
FR2863198B1 (en) | 2006-03-03 |
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